对三种方法修理后复合材料蜂窝夹芯板的侧压性能进行了试验研究,结果表明,不同修理方法均可以有效恢复试件的侧压强度,所有试件侧压强度恢复率均在完好板强度的79％之上.使用k样本Anderson-Darling检验方法对试验结果进行分析,比较固化温度及固化设备等工艺因素对修理后试件力学性能的影响.结果表明:使用中温固化材料完成修理不会对修理结构的力学性能造成明显影响,同时使用热压罐完成修理区域固化通常可以改善修理后试件的力学性能,但改善程度与试件修理区域的有效高度密切相关；此外修理时要尽量避免非对称结构引起的附加弯矩对承载能力造成的不利影响.
参考文献
| [1] | 杜善义,关志东.我国大型客机先进复合材料应对策略思考[J].复合材料学报,2008,25(1):1-10.Du Shanyi,Guan Zhidong.Strategic considerations for development of advanced composite technology for large commercial aircraft in China[J].Acta Materiae Compositae Sinica,2008,25(1):1-10. |
| [2] | Boeing Ltd.Boeing 737-800 structural repair manual[S].USA:Boeing Ltd,2003. |
| [3] | Airbus Ltd.Airbus A320 structural repair manual[S].France:Airbus Ltd,2007. |
| [4] | Pipes R B,Adkins D W,Deaton J.Strength and repair of bonded scarf joints for repair of composite materials,NASA MSG 1304:16[R].Washington:NASA,1982. |
| [5] | Jones J S,Graves S R.Repair techniques for Celion-LARC-160 graphite-polyimide composite structures,NASA/CR-3794[R].Washington:NASA,1984. |
| [6] | Kumar S B,Sridhar I,Sivashanker S I,et al.Tensile failure of adhesively bonded CFRP composites scarf joints[J].Materials Science and Engineering B,2006,132:113-120. |
| [7] | Kumar S B,Sivashanker S I,Osiyemi S O,et al.Failure of aerospace composite scarf-joints subjected to uniaxial compression[J].Materials Science and Engineering A,2005,412:117-122. |
| [8] | Avery J L,Sankar B V.Compressive failure of sandwich beams with debonded face-sheets[J].Journal of Composite Materials,2000,34 (14):1176-1199. |
| [9] | Hansen Ⅰ.Compression behavior of FRP sandwich specimen with interface debonded[J].Journal of Composite Materials,1998,32 (4):335-360. |
| [10] | Tomblin J S,Salah L,Welch J M,et al.Bonded repair of aircraft composite sandwich structures,DOT/FAA/AR-03/74[R].Washington:U.S.Department of Transportation Federal Aviation Administration office of Aviation Research,2004. |
| [11] | Tomblin J S,Lacy T,Smith B,et al.Review of damage tolerance for composite sandwich airframe structures,DOT/FAA/AR-99/49[R].Washington:U.S.Department of Transportation Federal Aviation Administration office of Aviation Research,1999. |
| [12] | 汪海,陈秀华,郭杏林,等.复合材料蜂窝夹芯结构修理后强度研究[J].航空学报,2001,22(3):270-273.Wang Hai,Chen Xiuhua,Guo Xinglin,et al.Strength investigation of composite honeycomb structures after repair[J].Acta Aeronautica et Astronautica Sinica,2001,22 (3):270-273. |
| [13] | 赵美英,孙晓波,万小朋.蜂窝夹芯结构板芯脱胶修补研究[J].航空学报,2003,24(5):474-476.Zhao Meiying,Sun Xiaobo,Wan Xiaopeng.Strength investigation of repaired composite honeycomb structure with unbounded damage[J].Acta Aeronautica et Astronautica Sinica,2003,24(5):474-476. |
| [14] | 周银华,赵英美,王瑜,等.含穿透损伤复合材料蜂窝夹芯修补结构强度分析[J].西北工业大学学报,2011,29(4):536-541.Zhou Yinhua,Zhao Yingmei,Wang Yu,et al.Finite element analysis of composite honeycomb sandwich structure with penetrated damage and its repaired structure[J].Journal of Northwestern Polytechnical University,2011,29 (4):536-541. |
| [15] | Armstrong K B,Bevan L G,Cole Ⅱ W F.Care and repair of advanced composites[M].2nd edition.PA USA:SAE International,2005:263-265. |
| [16] | Scholz F W,Stephens M A.K-sample Anderson-Darling tests of fit[J].American Statistical Association,1987,82:918-924. |
| [17] | Department of Defense.MIL-HDBK-17-1G polymer matrix composites guidelines for characterization of structural materials[M].Washington PA USA:Materials Sciences Corporation,MIL-HDBK-17 Secretariat,2009:465-586. |
| [18] | 中国航空工业集团公司.HB 7618-2009聚合物基复合材料力学性能数据表达准则[S].北京:国防科学技术工业委员会,2009.Aviation Industry Corporation of China.HB 7618-2009 Data presentation principal of mechanical properties for polymer matrix composite materials[S].Beijing:Commission of Science,Technology and Industry for National Defense,2009. |
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